Accession Number : AD0854739
Title : Effects of External Source Radiation on the Stagnation Flow and Heating of a Hypersonic Missile,
Corporate Author : ARMY MISSILE COMMAND REDSTONE ARSENAL AL SYSTEMS RESEARCH DIRECTORATE
Personal Author(s) : Lilly, Julius Q.
Report Date : 29 MAY 1969
Pagination or Media Count : 103
Abstract : In this investigation, the effects of external source radiation on the viscous hypersonic shock layer are analyzed. The problem corresponds to the condition that could be encountered by a hypersonic missile in flight near a nuclear blast. The conservation equations are solved for a viscous, hypersonic, radiating stagnation region flow by a similarity method. The radiative heat flux is obtained for the plane parallel slab approximation considering emission and absorption of radiation in the shock layer. A two-step model approximation to the spectral absorption coefficient of air is developed from detailed spectral data and used in this investigation. Real gas thermodynamic and transport properties are utilized in the form of correlation equations. Numerical solutions are presented for free stream conditions of 0.1 atm pressure, 1000K temperature, 1000 Btu/sq ft-sec external radiative flux, and flight velocities of 10,000, 20,000, and 30,000 ft/sec for nose radii between 0.1 and 1.0 foot. The body temperature is held constant at 2000K. (Author)
Descriptors : (*ANTIMISSILE DEFENSE SYSTEMS, NUCLEAR EXPLOSIONS), (*REENTRY VEHICLES, THERMAL RADIATION), BLAST, HYPERSONIC CHARACTERISTICS, BLUNT BODIES, STAGNATION POINT, CONVECTION(HEAT TRANSFER), THERMODYNAMICS, VISCOSITY, FROZEN EQUILIBRIUM FLOW, PRANDTL NUMBER, HEAT FLUX, TRANSPORT PROPERTIES.
Subject Categories : Antimissile Defense Systems
Guided Missile Reentry Vehicles
Distribution Statement : APPROVED FOR PUBLIC RELEASE